Aeroplane



Sept 18 41923' H B QHIELDS AEROPLANE Filed April V, 1921 5 Sheets-Sheet 2 A L46829 Sept' 18 1923 H. B. SHIELDS AEROPLANE n Filed April 7, 1921 5 Sheets-Sheet 3 ,4 w .5. j I 5 o I nvmrfoz mi IW? Henri.; Bhlds 5 Sheets-Sheet 4 H.' B. SHIELDS AERO'PLANE Filed April '7. 1921 N mv mw QR NN Sept. 18

E H2153 El. hields Sept. 18 1923. 1,468,329

- H. B. sHlELDs v 'AEROPLANE Fil-ed April v. 1921 5 sheets-sheet 5 Z5 T g5.

zzzzw Het@ hhiald Patente Sept.. 18, 1923o HENRY B. SHIELDS, 0F

naar

irrio FREEPORT', NEW YORK.

AEROPLANE.

Application led April 7,

To all whom it may concern:

Be it known that I, HENRY B. SHrELDs, a citizen of the United States, residin at Freeport, in the county of Nassau and tate of New York, have invented certain new and useful Improvements in Aeroplanes, of which the following isa specification.

This invention relates to aeroplanes, and the primary objects of the invention are; first, to provide, in an aeroplane, ainimproved means for increasing the lifting power of the aeroplane and at the same time decreasing the overall dimensions thereof; second, to provide an improved means for forming and arranging the controlling surfaces, so that the same will form a part of the sustaining surfaces, whereby the same will not only act as to support their own weight but also help to support the weigh of other parts of the aeroplane.

Another object of the invention is to provide an improved aeroplane, which is particularly adapted for commercial work, owing to the fact that the novel plane or aerofoil construction, permits a relatively large amount of weight to be carried.

A further object of the invention is to provide a novel wing or aerofoil construction for aeroplanes, which is relatively narrow and which embodies a series of suerposed aerofoils, forming a relatively arge supporting active surface, with a relatively small overall surface.

A further object of the invention is to pnovide a novel means for arranging the aerofoils or planes in the wing construction, and a novel means for bracing and supporting said aerofils or planes.

A still further object of the invention is to provide an improved aeroplane embodying a plurality of spaced rows of wings, each of the wings including superposed planes of relatively small chord, certain rows of the wings, arranged adjacent to the front and rear of the plane, being so oonstructed as to act as ailerons and elevators and the like.

A still further object of the invention is to provide a novel means for operating the said movable wings, so as to permit the ready and easy control ofthe aeroplane.

lVith these and other objects in view, the invention consists in the novel construction, arrangement and formation of parts, as

1921. Serial No. 459,451.

will be hereinafter more specifically described, claimed and illustrated in the accompanying drawings. forming a part of this specification, in which drawings:

Figure l is a side elevation of the improved aeroplane.

Figure 2 is a top plan view of the improved aeroplane.

Figure 3 is a front elevation of the improved aeroplane.

Figllre 4 is an enlarged fragmentary view of one of the rear wings of the plane showing the means in which the movable planes or aerofoils are mounted therein for controlling the fiight of the aeroplane.

Figure 5 is an enlarged fragmentary vertical section taken on the line 5,-5 of Figj ure 3 illustrating the means for mounting the movable planes or aerofoils in the front wing construction.

Figure 6 is an enlarged fragmentary front elevation of one of the forward wings, showing the means for moving the adjustable planes or aerofoils.

Figure 7 is a detail horizontal section taken on the line 7 7 of Figure 5, illustrating the means of pivotally connecting the movable planes or aerofoils to the supporting struts or strips.

Figure 8 is an enlarged fragmentary transverse section through the rearmost Wing structure, showing the means of mounting the rudder and balancing planes therein.

Figure 9 is a fragmentary front elevation of one of the wings embodying the stationary planes or aerofoils.

Figure l0 is a detail transverse section y through the same.

Figure ll is a diagrammatic perspective view of the controlling means for the movable planes of the front and rear wings.

Referring to the drawings in detail, wherein similar reference characters designate corresponding parts throughout the several views, the letter A indicates the body or fuselage of the aeroplane.; B, the forward pair of wings; C and D the rear wings; E, the intermediate wings; F, the landing gear; and G the controlling means for the movable portions of the wings B, C and D as will be hereinafter more fully described. The body or fuselage A has been shown extending longitudinally 0f 19h@ flfoplane and of a.

substantially cigar shape, but it is to be understood that the particular shape ofthe body or fuselage may be departed from without departing from the spirit or scope of the present invention. If so desired, a series of bodies may be utilized instead of the single body, and in this instance the same may be connected together in any preferred manner. While as stated, the body A may be of any construction, it is preferred that the same include the inner and outer skins 15 and 16 held in spaced relation by annular bulk heads 17. The terminals of the body carry suitable pulling and pushing propellers 18 and 19, which can be driven in any preferred manner from a series of engines which can be arranged in the body in any preferred way. lt is to be understood also, that the body A can be divided into suitable compartments for the comfort of passengers and for the purpose oi carr ing car o,

While the wings B (J lg, and are all ot substantially the same construction, inasmuch as each of the same includes a plurality of superposed rows or banks ot planes or aerofoils, the front pair of wings B are provided with movable planes or aerofoils 20 and 21 arranged on opposite sides of the body, while the rear wings C and D are provided with a plurality of movable planes r or aerofoils 22 and 23 arranged on opposite sides of the body A. These or aerofoils form means for flight of the aeroplane and nate the necessity of providing the usual ailerons, stabilizers and elevators.

Each of the wings B, C, D, and E include upper and lower truss beams or spars 24 and 25. These upper and lower truss frames or spars 24 and 25 extend transversely across the aeroplane and are arranged in spaced relation to the body or fuselage A therefor. I hese spars are of a truss or braced constructlon so as to give strength and rigidity thereto without;v undue weight and includes the upper and lower strength members 26 and 27, which are preferably cambered or of a streamline form. These upper and lower members 26 and 27 are braced by diagonally movable, planes controlling the `extending strips 28, which may be connected by suitable angle irons 29 and 30 together and to theupper and` lower strength members 26 and 27. The upper and lower spars or truss frames 24 and 25 are connected to the body or fuselage A by means of radially extending upper and ower com ression members 31 and 32, which may e constructed the same as the truss members or spars 24 and 25. The inner terminals of the compression radial members 31 and 32 can be connected to the annular bulk heads 17 by means of suitable clips or bracket members 33. As shown these brackets or clips 33 are extended through the outer skin 16 of the fuselage A.. llhe upper and lower truss entirely elimiframes or spars 24 and 25 are also connected by vertical truss or compression struts 34 and these compression frames or struts may be of the same construction as the radial compression members 31 and 32. The spars 24`and 25 ma be further connected by diagconstruction 38 interposed therein if so del sired.

Arranged between the s ars or truss frames 24 and 25 oi each of t e wings B, C, l), and E are arranged the banks or super- )osed series of planes or aerofoils as will be hereinafter more fully described, and the front pair of wings Bare provided with a series of stationary planes or aerofoils designated by the numeral 39 and with the movable series of planes or aerofoils 20 and 21. The rear Ywings C and D are also provided with a series of rigid planes or aerofoils 40 and the series or banks of movable pla-nes or aerofoils 22 and 23. The intermediate wings E are merely provided With the rigid planes or aerofoils 41, as will be apparent as the description proceeds.

The rigid planes or aerofoils 39, 40 and 41 are of relatively small chord as are the movable lanes or aerofoils 20, 21, 22 and 23, and t e rigid planes or aerofoils extend relatively close together, and are arranged in d1- rect alignment and extend all of the way from the lowermost spar or truss frame 25 to the uppermost spar or truss frame 24. lt is preferred that these rigid planes or aerofoils 39, 40 and 41 have their terminals bent at substantially right angles as at 43 and se' cured to the vertically disposed straps 44, which in turn have their terminals connected to the inner surfaces of the inner strips 27 of the truss frames or spars 24 and 25. ,'lhese vertically disposed straps 44 iorm means for supporting the rigid planes or aerofoils 39, 'l0 and 41. It can be seen that the tension cables 35 are arranged in llO the rigid and movable planes or aerofoils. ln the forward pair of wings B and the rear wings C and D, the movable planes or ailerons 20, 21, 22 and 23 are arranged on opposite sides of the fuselage A and act as the elevators and ailerons of the aeroplane. As

shown the movable planes or aerofoils do not extend the entire length of the wings, but terminate short thereof, and this space is occupied by the rigid planes or aerofoils which have heretobefore been described. The movable banks or series of planes or aerofoils 20, 21 and 22 and 23 are of substantially' the same construction, and a description of one is deemed sulicient for all. As shown these planes or aerofoils are of small chord and have their forward or leading edges connected to forward vertically disposed straps or strips 45 which take the place of vertical straps or strips 44. The forward edges of the movable planes or aerofoils are provided with hinged members 46, which are provided with laterally projecting pintles 47, which are in turn placed in suitable bearing openings formed in the mentioned straps or strips 45.

The terminals of the vertical straps 44 are rigidly secured in any preferred manner to the upper and lower spars 24 and 25.

The trailing edges of the movable planes` or aerofoils are connected by means of the hinged brackets 48 to movable rear straps 49. These movable rear straps ,are in turn connected by means of pivot pins 50 with one angle 51 of bell cranks 52. The upper angles of these bell cranks 52 are connected by means of pivot pins 53 with 'the lower surface of the uppermost truss frame or spar 24. The lower end of the straps 49 are connected in turn to one angle of the bell cranks 54, which are of the same construction as the upper bell cranks 52, and these lower bell cranks 54 are in turn connected by means of suitable pivot pins to the lower spar 25. The innermost angles of the bell cranks 52 and 54 are connected by means of pivot pins 55 to upper and lower transversely extending operating rods 56 and 57 which are arranged longitudinally of the wings. It can be seen that by this construction, the movable planes or aerofoils on each side of the fuselage are connected together, so as to move synchronously. These rods 56 and 57 extend inwardly of the movable planes and are connected to the operating mechanism G as will be hereinafter more fully described. Intermediate the movable series or banks of planes or aerofoils 20, 21, 22 and 23 are arranged rigid planes or aerofoils 58, and these planes have their terminals connected to the radially extending truss members 31 and 32 and to suitable straps 59, which are connected to the fuselage and to the spars 24 and 25.

The rearmost wing D is provided, on the opposite sides of the fuselage A with a pair of balanced planes 60, and these balanced planes 60 are of a relatively larger chord than the planes or aerofoils heretobefore described, and tend to prevent what is comf monly known as stalling. If so desired, portions of the'usual planes may be omitted as the planes 60 will perform their functions. As shown these balanced planes are interposed between the movable planes 22 and 23 carried by the rearmost wings D. These balanced planes extend beyond the f-orward and trailing edges of the planes or aerofoils and are provided with longitudinally extending shafts 61 which are mounted in suitable bearings 62 carried by the compression struts 34 and by the annular bulk head 17 of the fuselage. In order to accommodate the front and rear straps 45 and 49 of the movable planes or aerofoils 22 and 23 of the rearmost wing D, thev balanced planes 60 are provided with relatively large openings 64. This permits the balancing planes 6() to be readily moved, so as to change the angle thereof when necessary or desirable, without interfering with the straps.

In order to facilitate the steering of the aeroplane, rudders 65 are arranged on opposite sides of the fuselage A and these rudders have their inner ends provided with pintles 66, which are rotatably mounted in suitable bearing members 67, which also rotatably support the balanced planes 60. These bearing members 67 are secured to Y-shaped brace members 68, which are secured in any preferred manner to the fuselage A. The Y-shaped brace members 68 form effective means for supporting the rudders 65. The upper terminals of the rudders 65 are also provided with pintles 69 which are mounted in bearing members 70 carried by the inner surfaces of the upper and lower truss frames or spars 24 and 25.

The upper and lower ends of the tension cables 35 'and 37 may be connected in any preferred manner to the truss frame or spars 24 and 25, and as shown the cable terminals are provided with eyes 70', which may be connected to suitable brackets 71, i

which may be connected to the leading and trailing edges of the brace members or struts 26.

The landing gear F for the aeroplane may be of any preferred construction, and as shown a plurality of landing wheels 72 are provided, which are mounted upon suitable angle members 73, which can be secured adjacent to their angle by means of pivot pins 74 to the lower truss members or spars 25 if so desired. The upper terminals of these angle members 73 may be connected to the fuselage or the wings by suitable tension cables or the like 75.'

If found desirable, the wings C and D can be connected together by means of suitable longitudinally extending or diagonally disposed stay wires or the like 76, and certain of the front and rear wings may be connected by means of cables or tension wires 77 to the front and rear portions of the fuselage. t

The mechanism G for operating the movable planes or aerofoils 20, 21, 22 and 23 and the balance planes 60 has been shown diagrammatically and it is to be understood that this construction may be changed in any desired manner as well as the arrange-- ment shown for supporting the rigid planes the wings B, C, and

or the hinged planes, providing the same does not depart from the spirit or scope of the claims.

In brief, the controlwhich'is now to be described, is so arranged that when it is desired to move the aeroplane downward, the same is moved in one direction and the movable planes 2O and 2l of the wings B will be moved at a smaller angle of incidence,

while the movable planes and the balancing planes 60 yin the wings C and D will be simultaneously moved to the larger angle of incidence. This will cause less lift at the .front and more lift at the rear of the aeroplane, causing it to dive. The control is so constructed'that reverse movement of the same will cause a reversal of the movement of the movable planes which will cause the nose of the aeroplane to rise. The control is so constructed that when it is desired to vary the lateral course of the aeroplane, the movable aerofoils or planes on one side of can be moved to a smaller angle of incidence, while the mov able planes or aerofoils on the opposite sidesTof the wings B, C, and D can be simultaneously moved to a larger angle of incidence, thus giving greater support on one side or the other` as desired.

In carrying out the control, the shafts 61 are extended into the fuselage A and are provided with the cranks 78 for connection with the operating mechanism. The operating rods 56 and 57 of the movable planes or aerofoils 21, 22, 23 are also extended to the substantially central portion of the wings, andthe upper rods 56 are connected to the lower angles of bell cranks 79, which have their other angles pivotally connected to the inner surface of the upper truss frame or spar 24. The bell cranks 79 .f for the inner ends of the movable planes 20 'on opposite side of the body 'are arranged in opposite directions, as clearly shown in Figure 4 of the drawings andin the diagrammaticview. The lower control rods 57 are also connected to the innermost angle ofthe bell cranks 80, and the outermost angle of the bell crank are pivotallyfconnected to the inner surface of the lower spar 25. The bell crank 80 of the rods 57 are also arranged in opposite directions to each other as clearly shown in Figure 11.

The control mechanism G includes a U- shaped bridge member 85, which is mounted for swinging movement on a horizontal pivot' 86 toward the front and rear of the aeroplane. This horizontal pivot may be mounted in suitable bearingsf'87 carried by any suitable portion of .the plane. This U- shaped bridge member 85' constitutes the operating means proper for controlling the raising and lowering of the aeroplane, and has rotatably mounted thereon a suitable steering wheel 88 which carries a drum 89,

and this steering wheel 88 constitutes the means for altering the lateral course' of the plane. In view of the fact that the same planes or aerofoils are used both for elevator and aileron effect, this necessitates the introduction of the differential mechanism between the control bridge member 85 and the operating cables which will be hereinafter more iiilly described. This diiferential mechanism is designated by the numeral 90.

The differential mechanism 90 includes a double ended lever 91, which is rotatably mounted upon a vertically disposed shaft 92. The terminals of the double ended lever 91 has secured thereto suitable'pulleys 93 and 94 respectively. The shaft 92'also has rotatably mounted thereon a drum 95 which has secured thereto an operating crank 96. This crank may also be mounted upon the shaft 92. The bridge 85 has a cable 97 attached intermediate its ends, as at 98, to' the forward end of the crank 96, and the opposite terminals of this cable 97 are connected respectively to the arms of the bridge 85 above and below the horizontal pivot 86 thereof. Thus it can be seen that when the bridge is rocked in one direction, a pull will be made upon one run of the cable 97 and a slack on the other run, and when the bridge is rocked in the opposite direction a pull will be exerted on the opposite run and a slack on the other run. In order to permit of the operation of the planesl or aerofoils 20, and the planes or aerofoils -23 and balancing plane 60, on one side, a cable 100 is secured to the crank 79 to which the rod 56 of the planes or aerofoils 20 are secured. This cable 100 is trained around a guide pulley 101, around the pulley 93 carried by the two armed lever 91, around the drum 95, back around the pulley 93, around suitable guide pulleys 102 to the bell crank 79 of the upper operating rod 56 for the planes 23. This cable also has secured thereto a branch cable 103 which is attached to the uppermost terminal of the crank 78 of the planes. It can be seen that upon operation of this cable, the planes 20 and 23 will `be moved in opposite directions,v This movement is further augmented and insured by a cable 105, which is 'secured to the bell crank 80 of the planes oraerofoils 20 and trained around suitable guide pulleys 106 to the lower crank 80 of the lowermost rod 57 of the planes or aerofoils 23. In order to permit the operation of the planes or aerofoils 21 and 22, a cable 110 is provided. This cable 110 has one terminal attached to the bell crank 79 of the uppermost operating 7.rod 56 of the lanes or aerofoils 21 and is trained aroun suitable guide -pulleys 111 and has its opposite terminals secured to the bell crank 79 of the operating rod 56 of the planes or aerofeils 22,. The intermediate vaa l of incidence.

portion of this operating cable is trained around the pulley 94 around the drum 95 and then crossed and brought around the pulley 94. It can be seen that. when this cable is actuated, the planes or aerofoils 21 and 22 will be operated in opposite directions. In order to lnsure this movement., the cable 115 is provided and this cable is trained around suitable guide pulleys 116 and has its forward terminals secured to the lowermost bell crank 80 of the rod 57 of the planes or aerofoils 21 and its rearmost terminals secured to the lowermost. crank 80 ot the operating rod 57 of the planes or aerofoils 22. This cable 115 has also connected thereto a branch cable 117, which is attached to the lower end of the balance 60 and the cable 100 also has a branch cable 103 attached thereto which is secured to the upper end of the crank 78 of the balance plane 60 interposed in the planes or aerofoils 23. The cable 105 also has a branch cable 108 secured thereto which is attached to the lowermost end ofthe crank 78 of the balance plane 60 interposed in the planes or aerofoils 23. It can be seen that when the bridge 85 is rocked in a forward direction, the aerofoils 20 and 21 will be lowered toa less angle of incidence, while the aerofoils of the planes 22 and 23 at the rear of the aeroplane will be inclined upwardl at a greater angle This wil permit the ready guiding of the aeroplane. Upon the rear movement of the bridge, the movement of the aerofoils 20, 21, 22 and 23 will be reversed, and the aeroplane will take an upward course. When it is desired to change the lateral course of the aeroplane, thel wheel 88 is moved, which will operate simultane- -ousl the aerofoils 20 and 22 on one side of t e plane and the aerofoils 21 and 23 on the other side of the aeroplane. The planes of the aerofoils 20 and 22 move in the same direction, and the aerofoils 21 and 23 move in the same directionbut opposite to the planes 20 and 22. A cable 120 is provided and has its terminals secured to the double lever 91 on opposite sides of the vertical shaft 92 and the intermediate portion of this cable is coiled around the drum 89. It can be seen that upon operation of the wheel 88, the cables 100 and 110 will be moved in opposite directions which will actuate the planes on opposite sides of the aeroplanes in opposite directions, which will cause more lift on one side of the plane than on the other.

.seen that an aeroplane o sion, and which is capable of lifting a very lar e dead weight. l

hange's of details may be made without departing from the spirit or scope of this invention; but, v

I claim:

1. l'n an aeroplane. a body, an upper and lower spar arranged transversely of the body, compression and tension members connecting the spars together and to the body, a series of superposed aerofoils arranged between the spars, compression members connecting the aerofoils to the spars, and to cach other, a plurality of series of aerofoils arranged in rear of the first series of aerofoils arranged in spaced relation along the body in the line of Hight, certain portions of said series of aerofoils being hinged for swinging movement, whereby the same can be used as ailerons and elevators, and aero foils having relatively larger chord than the first mentioned aerofoils arranged in certain of the series of aerotoils.

2, In an aeroplane, a body, a series of banks of superposed aerofoils, arranged in spaced relation along the body in the line of flight, certain portions of said series of aerofoils being hinged whereby the same can be used as both ailerons and elevators, relatively large aerofoils arranged in certain of the series adapted for use as stabilizers and elevators and supporting surfaces.

3. In an aeroplane, a body, a forward series of superposed aerofoils carried by the body, a plurality of rear series of superposed aerofoils carried by the rear portion of the body, a series of superposed aerofoils carried by the body and arranged intermediate the 100 front and rear series of aerofoils, certain of the aerofoils of the front and rear series at the opposite sides of the body being hinged, whereby the same can be used as ailerons and elevators, the hinged series of 105 aerofoils at the front portion of the aeroplane on one side of the body arranged to move oppositely to the rear series of hinged aerofoils on the opposite diagonal side, the series of aerofoils at the front of the aero- 110 plane opposite to the mentioned front aerofoils being adapted to move in opposite direction to the rear series of hinged aerofoils diagonally opposite thereto and means for operating said hinged aerofoils.

4. In an aeroplane, a plurality of wings arranged in equi-distantly spaced relation, each of said wings including an u pper and lower spar, compression and tension members connecting the spars together and to 120 the body, the front and rear wings having the opposite ends thereof provlded with a plurality of rigid superposed planes of. relatively narrow chord, a plurality of hinged superposed planes of relatively narrow 125 chord arranged in the space between the -body and the rigid end planes, means connecting the hinged planes together for synchronous movement on each side of the body, and means for operating said hinged planes.

e and interposed in the pivoted planes of said 5. In an aeroplane, a longitudinally eX- tending body, a plurality of equi-distantly spaced wings arranged transversely of the body in the line of flight, pusher and puller propellers carried by the body, the front and rear Wings including a series of superposed rigid planes of relatively small chord arranged on opposite sides of the body in spaced relation thereto, and a plurality of superposed pivoted planes of relatively small chord arranged on opposite sides of the body and intermediate the body and the rigid planes, rudders carried by the rearmost Wing, and stabilizing` planes of relatively large chord carried by the 'rearlnost Wing rearmost Wing.

6. In an aeroplane, a body, one or more supporting structures attached to the body, a row or series of superposed aerofoils supported by said structure near the front of the body, a plurality of series of superposed aerofoils supported by said structure and arranged in the rear of the first mentioned row.

or series of aerofoils, certain portions of which aerofoils may be pivoted :for use as ailerons or eleva-tors, or for both functions, and Which may have larger aerofoils introduced into its construction for use as sup'- porting surfaces, ailerons, elevators, rudders or stabilizers, and means for operating said hinged or auxiliary surfaces.

7 In an aeroplane, a body, a plurality of spaced rows of supportin structures carried by the body, a series o superposedcaerofoils supported by the foremost supporting structure, a series of superposed aerofoils carried by the supporting structures in rear of the foremost supporting structure, certain portions of 'said last mentioned series of aerofols being hinged for swinging movement for use as ailerons and elevators, relatively wide swinging aerofoils introduced into the pivoted portions of the aerofoils, whereby the same can be used as supporting surfaces, ailerons, elevators, rudders and stabilizers, and means for operating the swinging first and second mentioned aero foils.

HENRY B. SHIELDS. 

